Method and apparatus for resin transfer molding composite parts

ABSTRACT

A composite fabrication apparatus which may include a first tooling die and a second tooling die movable with respect to each other; a temperature control system having induction coils disposed in thermal contact with the first tooling die and the second tooling die; a first die susceptor provided on the first tooling die and a second die susceptor provided on the second tooling die and connected to the induction coils; and a cooling system disposed in thermal contact with the first tooling die and the second tooling die. A resin transfer system delivers resin from a resin source to the tooling dies to allow resin transfer molding. A composite fabrication method is also disclosed.

CROSS REFERENCE TO RELATED APPLICATIONS

This application is a continuation-in-part of U.S. patent applicationSer. No. 11/854,733 filed Sep. 13, 2007.

TECHNICAL FIELD

The disclosure generally relates to composite fabrication apparatus andmethods, and deals more particularly with a resin transfer moldingapparatus and method that optimizes the performance of a moldedcomposite part.

BACKGROUND

Processing techniques and facilities that enable widespread use of resintransfer molded composite components at rates and costs that allowsignificant weight savings scenarios are desirable in some applications.The capability to rapidly heat, consolidate and cool in a controlledmanner may be required for high production rates of compositecomponents. Current processing techniques include the use of heateddies, and therefore, may not allow for the optimum controlled cool-downwhich may be required optimized fabrication. Furthermore, currentprocessing techniques may have limitations in forming the desiredcomponents since such techniques may have limitations in the capabilityto establish optimal thermal cycles to meet both producability andaffordability goals while establishing the optimal material properties.

SUMMARY

The disclosed embodiments provide a method and apparatus for resintransfer molding composite parts that provides rapid heating and cooldown of the part by using tooling that has a relatively small thermalmass which is directly coupled to a temperature control system.Contoured susceptors forming a mold cavity are inductively coupled withelectric coils that rapidly heat the susceptors, allowing precisetailoring of thermal and pressure profiles. The temperature controlsystem also includes means for rapidly cooling the susceptors to enhanceprocess control. The susceptors are configured to allow the flow ofresin into the mold cavity using a resin transfer system.

According to one disclosed embodiment, a resin transfer moldingapparatus is provided comprising: a pair of tooling dies each includinga plurality of stacked metal sheets; first and second susceptorsrespectively mounted on the first and second dies, and includingcontoured surfaces defining a mold cavity for molding a part; atemperature control system including induction coils inductively coupledwith the first and second susceptors; and, a resin transfer system fordelivering resin from a resin source to the mold cavity. The toolingdies may include contoured faces respectively matching the contouredsurfaces of the susceptors. A dielectric shell may be disposed betweenthe susceptors and the corresponding tooling dies. The stacked metalsheets may be spaced apart to define air gaps through which a coolantmay flow in order to provide rapid cool down of the susceptors.

According to another disclosed embodiment, a resin transfer moldingapparatus is provided, comprising a pair of tooling dies respectivelyincluding matching contoured faces and a plurality of passagewaysextending generally transverse to the contoured faces; first and secondsusceptors respectively mounted on the contoured faces of the toolingdies and including contoured surfaces defining a mold cavity for moldinga part; a temperature control system; and, a resin transfer systemcoupled with the tooling dies for delivering resin from a resin sourceto the mold cavity. The temperature control system may include inductioncoils inductively coupled with the first and second susceptors forheating the susceptors. The temperature control system may furthercontrol means for delivering coolant through the passageways to cool thefirst and second susceptors. The apparatus may further include adielectric shell disposed between each of the susceptors and acorresponding tooling die. The tooling dies may include a plurality ofstacked metal sheets, wherein the passageways are defined between themetal sheets. The susceptors may include one or more openings that allowinflow of resin into the mold cavity, and venting of excess resin fromthe mold cavity.

According to a disclosed method embodiment, molding a composite partcomprises the steps of: placing susceptors in a mold cavity; introducinga fiber preform into the mold cavity, in contact with the susceptors;heating the mold cavity by inductively heating the susceptors; infusingthe preform with resin to form a part by transferring resin from a resinsource into the mold cavity; cooling the part by cooling the susceptors;and, removing the part after the part has been cooled. The part may becooled by flowing a cooling medium over the susceptors. The coolingmedium may be delivered to the susceptors through passageways in a die.The resin may be transferred from the resin source through one or moreopenings in one of the susceptors.

Other features, benefits and advantages of the disclosed embodimentswill become apparent from the following description of embodiments, whenviewed in accordance with the attached drawings and appended claims

BRIEF DESCRIPTION OF THE ILLUSTRATIONS

FIG. 1 is a sectional view of a pair of tooling dies of a stackedtooling apparatus, with molding compounds positioned between the toolingdies.

FIG. 2 is a sectional view of a pair of tooling dies, with the moldingcompounds enclosed between a pair of die susceptors provided on thetooling dies.

FIG. 3 is a sectional view of the tooling dies, with the tooling diesapplying pressure to form and consolidate a composite sheet.

FIG. 4 is a sectional view of the tooling dies, with the tooling diesclosed against the die susceptors and composite sheet and a coolingsystem engaged to cool the tooling dies.

FIG. 5 is a sectional view of the tooling dies, with the tooling diesand die susceptors released from the composite sheet after forming andcooling of the composite sheet.

FIG. 6 is a schematic view of a tooling die, more particularlyillustrating a die susceptor and die liner provided on the engagingsurface of the tooling die and multiple induction coils extendingthrough the tooling die.

FIG. 7 is a front sectional view of a tooling die, more particularlyillustrating multiple induction coils and multiple thermal expansionslots provided in the metal sheet.

FIG. 8 is a functional block diagram of an alternate embodiment of aresin transfer molding apparatus.

FIG. 9 is a sectional view illustrating the apparatus of FIG. 8, thetooling dies having been opened and a preform having been loaded intothe mold cavity.

FIG. 10 is a sectional view of the susceptors forming part of thetooling dies shown in FIG. 9, and better depicting openings in thesusceptors through which resin may flow into and out of the mold cavity.

FIG. 11 is a sectional view similar to FIG. 9, but showing the dieshaving been closed in order to apply pressure to form and consolidatethe resin infused preform.

FIG. 12 is a sectional view similar to FIG. 11 but showing a coolingsystem having been engaged to cool the part.

FIG. 13 is a sectional view showing the dies having been opened and afully formed part being removed from the mold cavity.

FIG. 14 is a flow diagram illustrating the steps of a method for resintransfer molding a composite part.

FIG. 15 is a flow diagram of an aircraft production and servicemethodology.

FIG. 16 is a block diagram of an aircraft.

DETAILED DESCRIPTION

Referring initially to FIGS. 1-7 of the drawings, a stacked toolingapparatus which is suitable for implementation of the compositefabrication method is generally indicated by reference numeral 1. Thestacked tooling apparatus 1 may include a first die frame 2 and a seconddie frame 8. A first tooling die 3 may be provided on the first dieframe 2, and a second tooling die 9 may be provided on the second dieframe 8. The first tooling die 3 and the second tooling die 9 may behydraulically-actuated to facilitate movement of the first tooling die 3and the second tooling die 9 toward and away from each other. The firsttooling die 3 may have a first contoured die surface 4, whereas thesecond tooling die 9 may have a second contoured die surface 10 which iscomplementary to the first contoured die surface 4 of the first toolingdie 3.

As shown in FIG. 6, multiple induction coils 26 may extend through eachof the first tooling die 3 (and the second tooling die 9, not shown) tofacilitate selective heating of the first tooling die 3 and the secondtooling die 9. A temperature control system 27 may be connected to theinduction coils 26. A first die susceptor 20 may be thermally coupled tothe induction coils 26 of the first tooling die 3. A second diesusceptor 21 may be thermally coupled to the induction coils 26 of thesecond tooling die 9. Each of the first die susceptor 20 and the seconddie susceptor 21 may be a thermally-conductive material such as, but notlimited to, a ferromagnetic material, cobalt, nickel, or compoundsthereof. As shown in FIGS. 1-5, the first die susceptor 20 may generallyconform to the first contoured die surface 4 and the second diesusceptor 21 may generally conform to the second contoured die surface10.

As shown in FIG. 6, an electrically and thermally insulative coating 30may be provided on the first contoured die surface 4 of the firsttooling die 3, as shown, and on the second contoured die surface 10 ofthe second tooling die 9. The electrically and thermally insulativecoating 30 may be, for example, alumina or silicon carbide. The firstdie susceptor 20 may be provided on the electrically and thermallyinsulative coating of the first tooling die 3, as shown, and the seconddie susceptor 21 may be provided on the electrically and thermallyinsulative coating 30 of the second tooling die 9.

As shown in FIGS. 1-5, a cooling system 14 may be provided in each ofthe first tooling die 3 and the second tooling die 9. The cooling system14 may include, for example, coolant conduits 15 which have a selecteddistribution throughout each of the first tooling die 3 and the secondtooling die 9. As shown in FIG. 4, the coolant conduit 15 may be adaptedto discharge a cooling medium 17 into the first tooling die 3 or thesecond tooling die 9. The cooling medium 17 may be a liquid, gas orgas/liquid mixture which may be applied as a mist or aerosol, forexample.

Each of the first tooling die 3 and the second tooling die 9 may eachinclude multiple stacked metal sheets 28 such as stainless steel whichare trimmed to the appropriate dimensions for the induction coils 26.This is shown in FIGS. 6 and 7. The stacked metal sheets 28 may beoriented in generally perpendicular relationship with respect to thefirst contoured die surface 4 and the second contoured die surface 10.Each metal sheet 28 may have a thickness of from about 1/16″ to about¼″, for example and preferably ⅛″. An air gap 29 may be provided betweenadjacent stacked metal sheets 28 to facilitate cooling of the firsttooling die 3 and the second tooling die 9. The stacked metal sheets 28may be attached to each other using clamps (not shown), fasteners (notshown) and/or other suitable technique known to those skilled in theart. The stacked metal sheets 28 may be selected based on theirelectrical and thermal properties and may be transparent to the magneticfield. An electrically insulating coating (not shown) may, optionally,be provided on each side of each stacked sheet 28 to prevent flow ofelectrical current between the stacked metal sheets 28. The insulatingcoating may be a material such as ceramic, for example, or other hightemperature resistant materials. However, if an air gap exists inbetweenthe stacked sheets, then no coating would be necessary. Multiple thermalexpansion slots 40 may be provided in each staked sheet 28, as shown inFIG. 6, to facilitate thermal expansion and contraction of the stackedtooling apparatus 1.

In typical implementation of the composite fabrication method, moldingcompounds 24 are initially positioned between the first tooling die 3and the second tooling die 9 of the stacked tooling apparatus 1, asshown in FIG. 1. The first tooling die 3 and the second tooling die 9are next moved toward each other, as shown in FIG. 2, as the inductioncoils 26 (FIG. 6) heat the first tooling die 3 and the second toolingdie 9 as well as the first die susceptor 20 and the second die susceptor21. Therefore, as the first tooling die 3 and the second tooling die 9close toward each other, the first die susceptor 20 and the second diesusceptor 21 rapidly heat the molding compounds 24. Thus, the moldingcompounds 24 which may be thermally molded as the first tooling die 3and the second tooling die 9 continue to approach and then close againstthe molding compounds 24, as shown in FIG. 2, forming the moldingcompounds 24 to the configuration of a composite sheet 25 (shown inFIGS. 3-5) which may be defined by the first contoured surface 4 of thefirst tooling die 3 and the second contoured surface 10 of the secondtooling die 9.

As shown in FIG. 4, the cooling system 14 is next operated to apply thecooling medium 17 to the first tooling die 3 and the second tooling die9 and to the first die susceptor 20 and the second die susceptor 21.Therefore, the cooling medium 17 actively and rapidly cools the firsttooling die 3 and the second tooling die 9 as well as the first diesusceptor 20 and the second die susceptor 21, also cooling the compositesheet 25 sandwiched between the first die susceptor 20 and the seconddie susceptor 21. The composite sheet 25 remains sandwiched between thefirst tooling die 3 and the second tooling die 9 for a predeterminedperiod of time until complete cooling of the composite sheet 25 hasoccurred. This allows the molded and consolidated composite sheet 25 toretain the structural shape which is defined by the first contouredsurface 4 and the second contoured surface 10 after the first toolingdie 3 and the second tooling die 9 are opened, as shown in FIG. 5. Theformed and cooled composite sheet 25 is removed from the stacked toolingapparatus 1 without loss of dimensional accuracy or delamination of thecomposite sheet 25 when it is cooled at an appropriateproperty-enhancing rate.

Attention is now directed to FIGS. 8-14 which illustrate a resintransfer mold apparatus 1 a that may be employed to mold a compositepart 58 a (FIG. 13). A pair of tooling dies 28 generally similar tothose described previously with respect to FIGS. 1-7, are respectivelysecured to molding press platens 42, 44, allowing the dies 28 to beopened and closed. Like the previously described embodiment, dies 28comprise a plurality of stacked metal sheets 28 a separated by air gapsthat form passageways 29 between the sheets 28 a. As previously pointedout, the use of spaced apart metal plates 28 a reduces the overallthermal mass of the die assembly 1 a and facilitates more rapid coolingof a formed part 58 a.

The dies 28 may include inductive heating coils 26 that are electricallyconnected together by a socket connection 45 when the dies 28 areclosed. The dies 28 have opposed surfaces that are contoured andgenerally match contoured mold surfaces 31 (FIG. 10) of a pair ofsusceptors 20 a, 21 a. The contoured molding surfaces 31 of thesusceptors 20 a, 21 a match those of the finished composite part 58 a,and form a molding cavity 33. The susceptors 20 a, 21 a are electricallyinsulated from the dies 28 by respectively associated dielectric shells46, 48 which may comprise, for example, without limitation, alumina orsilicon carbide. The susceptors 20 a, 21 a may comprise a thermallyconductive material such as, but not limited to, a ferromagneticmaterial, cobalt, nickel or compounds thereof. A water cooled shoe 53contacts the lower peripheral edges of the susceptors 20 a, 21 a to aidin cooling the susceptors 20 a, 21 a, as will be described below. Thecoils 26 as well as a cooling system 14 are controlled by a suitabletemperature control system 65 that control heating up and cooling downthe susceptors 20 a, 21 a.

A resin transfer system 55 comprises a source of resin along with thepump 50 for transferring resin to the mold assembly 1 a. In some cases,a catalyst may be added to the resin which is combined and mixed at amixing head 52 before being delivered through a supply line 54 to themold cavity 33. The resin may comprise any of the resins typically usedin resin transfer molding, including, but not limited to, polyester,vinylester, epoxy, phenolic and methyl methacylates, which may includepigments and fillers, if required.

As shown in FIG. 9, the resin supply line 54 is connected to alignedopenings 47 in susceptor 20 a and dielectric shell 46. However, thesupply line 54 may be connected to the mold cavity 33 at other areas ofthe susceptor 20 a that would allow resin to flow into the mold cavity33. For example, the supply line 54 may be connected to openings (notshown) along a flange portion 57 of the susceptor 20 a.

In order to assure that the mold cavity 33 is completely filled withresin, a vent line 56 may be provided which allows excess or overflowresin to leave the mold cavity 33. In the illustrated example, the ventline 56 is connected to aligned openings 51 in a flange portion 61 ofthe susceptor 21 a and dielectric shell 48. Other techniques forallowing excess resin to be removed from the mold cavity 33, includingthe provision of a seal 59 that possesses characteristics such that itnormally seals the mold cavity 33 but yields slightly to allow theescape of excess or overflow resin from the mold cavity due to thepressure applied to the seal 59 by the pressurized resin. The seal 59may be formed from, for example, without limitation, an elastomermaterial.

Referring now simultaneously to FIGS. 8-14 a resin transfer moldingmethod begins at step 62 (FIG. 14) with the installation of thesusceptors 20 a, 21 a on the dies 28 and loading of a preform 58 intothe die cavity 33. The preform 58 may comprise a dry fiber reinforcementin the form of continuous strand, cloth, woven roving, long fibers orchopped strand, any of which may be, without limitation, glass, carbon,arimid or a combination thereof. FIG. 9 shows the susceptors 20 a, 21 ahaving been installed and a fiber preform 58 loaded into the mold cavity33. Next, at step 64, the dies 28 are closed as shown in FIG. 11,thereby closing the susceptor halves 20 a, 21 a, resulting in the moldcavity 33 being sealed. As the dies 28 close, the coils 26 areelectrically connected by the socket connections 45. The seal 59 sealsthe mold cavity 33 around the periphery of the susceptors 20 a, 21 a.With the susceptors 20 a, 21 a having been sealed, the mold cavity 33 isthen evacuated through vent 56 or other vacuum connections (not shown)that are connected to an evacuation system 63, creating negativepressure within the mold cavity 33.

At step 66, the induction coils 26 are energized, causing the susceptors20 a, 21 a to be inductively heated to temperature. When the susceptors20 a, 21 a have been heated to a threshold temperature, resin is pumpedfrom the source 50 through the mixing head 52, as shown at step 68, andflows into the mold cavity 33 through the supply line 54. The negativepressure within the mold cavity aids in drawing the resin into the moldcavity 33 from the supply line 54. The resin entering mold cavity 33flows through and infuses the dry preform 58. The resin continues toflow into the mold cavity 33 under pressure until the mold cavity 33 isfilled. Any excess resin may leave the mold cavity 33 through a ventline 56 or by passing across the seal 59 which may yield slightly,allowing the excess resin to flow therepass. The susceptors 20 a, 21 aremain at an elevated temperature as part of the process to cure theinfused preform 58 for the requisite period of time.

After the susceptors 20 a, 21 a have been held at the requisitetemperature for a prescribed length of time, the part 58 a is cooled atstep 70, as shown in FIGS. 12 and 14. This cooling process may includeengaging the cooling system 14 in which a cooling medium such as fluid,air, etc. is discharged from nozzles 15. The cooling medium flowsthrough the passageways 29, and passes over the surface of thedielectric shells 46 48, thereby cooling the susceptors 20 a, 21 a, andcarrying heat away from the finished part 58 a.

Finally, as shown in FIGS. 13 and 14, the remaining step 72 comprisesseparating the dies 28 and removing the finished part 58 a from the moldcavity 33. Since the susceptors 20 a, 21 a have been rapidly cooleddown, they may be quickly removed and exchanged for susceptors having adifferent contour in order to mold different parts and increaseproduction rate.

Referring next to FIGS. 15 and 16, embodiments of the disclosure may beused in the context of an aircraft manufacturing and service method 74as shown in FIG. 15 and an aircraft 76 as shown in FIG. 16. Aircraftapplications of the disclosed embodiments may include, for example,without limitation, composite stiffened members such as fuselage skins,wing skins, control surfaces, hatches, floor panels, door panels, accesspanels and empennages, to name a few. During pre-production, exemplarymethod 74 may include specification and design 78 of the aircraft 76 andmaterial procurement 80. During production, component and subassemblymanufacturing 82 and system integration 84 of the aircraft 76 takesplace. Thereafter, the aircraft 76 may go through certification anddelivery 86 in order to be placed in service 88. While in service by acustomer, the aircraft 76 is scheduled for routine maintenance andservice 90 (which may also include modification, reconfiguration,refurbishment, and so on).

Each of the processes of method 74 may be performed or carried out by asystem integrator, a third party, and/or an operator (e.g., a customer).For the purposes of this description, a system integrator may includewithout limitation any number of aircraft manufacturers and major-systemsubcontractors; a third party may include without limitation any numberof vendors, subcontractors, and suppliers; and an operator may be anairline, leasing company, military entity, service organization, and soon.

As shown in FIG. 16, the aircraft 76 produced by exemplary method 74 mayinclude an airframe 92 with a plurality of systems 94 and an interior96. Examples of high-level systems 94 include one or more of apropulsion system 98, an electrical system 100, a hydraulic system 102,and an environmental system 104. Any number of other systems may beincluded. Although an aerospace example is shown, the principles of theinvention may be applied to other industries, such as the automotiveindustry.

The apparatus embodied herein may be employed during any one or more ofthe stages of the production and service method 74. For example,components or subassemblies corresponding to production process 82 maybe fabricated or manufactured in a manner similar to components orsubassemblies produced while the aircraft 76 is in service. Also, one ormore apparatus embodiments may be utilized during the production stages82 and 84, for example, by substantially expediting assembly of orreducing the cost of an aircraft 76. Similarly, one or more apparatusembodiments may be utilized while the aircraft 76 is in service, forexample and without limitation, to maintenance and service 90.

Although the embodiments of this disclosure have been described withrespect to certain exemplary embodiments, it is to be understood thatthe specific embodiments are for purposes of illustration and notlimitation, as other variations will occur to those of skill in the art.

1. Resin transfer molding apparatus, comprising: a pair of tooling dieseach including a plurality of stacked metal sheets; first and secondsusceptors respectively mounted on the first and second dies, the firstand second susceptors including facing contoured surfaces defining amold cavity for molding a part; a temperature control system includinginduction coils inductively coupled with the first and secondsusceptors; and, a resin transfer system for delivering resin from aresin source to the mold cavity.
 2. The apparatus of claim 1, whereinthe temperature control system includes means for cooling the toolingdies.
 3. The apparatus of claim 2, wherein the cooling means includes:cooling passageways between the stacked metal plates, and means forintroducing a cooling medium into the passageways.
 4. The apparatus ofclaim 3, wherein the means for introducing the cooling medium includesnozzles in the passageways for directing the cooling medium toward thesusceptors.
 5. The apparatus of claim 1, wherein the tooling diesinclude contoured faces respectively generally matching the contouredsurfaces of the first and second susceptors.
 6. The apparatus of claim1, further comprising a dielectric shell disposed between each of thefirst and second susceptors and the corresponding tooling die.
 7. Theapparatus of claim 1 further wherein the metal sheets are spaced apartto define air gaps therebetween.
 8. The apparatus of claim 7, whereinthe temperature control system further includes means for introducing acooling medium into the air gaps.
 9. The apparatus of claim 1 whereineach of the stacked metal sheets includes an electrically insulatingcoating.
 10. The apparatus of claim 1 wherein each of the first and saidsecond susceptors comprises at least one material selected from thegroup consisting of a ferromagnetic material, cobalt, iron and nickel.11. The apparatus of claim 1 wherein at least one of the susceptorsincludes a vent therein to allow excess resin to escape from the moldcavity.
 12. The apparatus of claim 1 wherein at least one of thesusceptors includes an opening coupled with the resin transfer systemfor allowing resin to enter the mold cavity.
 13. The apparatus of claim1, further comprising an evacuation system for evacuating the moldcavity before resin is transfer by the resin transfer system to the moldcavity.
 14. The apparatus of claim 13, wherein at least one of thesusceptors include a vent therein coupled with the evacuation system.15. Resin transfer molding apparatus, comprising: a pair of tooling diesrespectively including matching contoured faces and a plurality ofpassageways extending generally transverse to the contoured faces; firstand second susceptors respectively mounted on the contoured faces of thetooling dies and including contoured surfaces defining a mold cavity formolding a part; a temperature control system including— a) inductioncoils inductively coupled with the first and second susceptors forheating the first and second susceptors, and b) means for deliveringcoolant though the passageways to cool the first and second susceptors;and, a resin transfer system coupled with the tooling dies fordelivering resin from a resin source to the mold cavity.
 16. Theapparatus of claim 15, further comprising a dielectric shell disposedbetween each of the first and second susceptors and a correspondingtooling die.
 17. The apparatus of claim 15, wherein each of the toolingdies includes a plurality of stacked metal sheets, and the passagewaysare defined between the metal sheets.
 18. The apparatus of claim 17,wherein each of the stacked metal sheets includes an electricallyinsulating coating.
 19. The apparatus of claim 15, wherein each of thefirst and said second susceptors comprises at least one materialselected from the group consisting of a ferromagnetic material, cobalt,iron and nickel.
 20. The apparatus of claim 15, wherein at least one ofthe first and second susceptors includes a vent therein to allow excessresin to escape from the mold cavity.
 21. The apparatus of claim 15,wherein at least one of the first and second susceptors includes anopening coupled with the resin transfer system for allowing resin toenter the mold cavity.
 22. The apparatus of claim 15, wherein thecoolant delivery means includes coolant conduits passing through thetooling dies.
 23. The apparatus of claim 22, wherein the coolantdelivery means includes nozzles coupled with the coolant conduits fordirecting the coolant through the passageways toward the susceptors. 24.The apparatus of claim 15 wherein at least one of the susceptorsincludes a vent therein to allow excess resin to escape from the moldcavity.
 25. The apparatus of claim 15 wherein at least one of thesusceptors includes an opening therein coupled with the resin transfersystem for allowing resin to enter the mold cavity.
 26. A method ofmolding a composite part, comprising the steps of: (A) placingsusceptors in a mold cavity; (B) introducing a fiber preform into themold cavity between the susceptors; (C) heating the mold cavity byinductively heating the susceptors; (D) infusing the preform with resinto form a part by transferring resin from a resin source into the moldcavity; (E) cooling the part by cooling the susceptors; and, (F)removing the part after the part has been cooled.
 27. The method ofclaim 26, further comprising the step of: (G) evacuating the mold cavitybefore step (D) is completed.
 28. The method of claim 26, wherein step(E) includes flowing a cooling medium over the susceptors.
 29. Themethod of claim 28, wherein step (E) includes delivering the coolingmedium to the susceptors through passageways in a die.
 30. The method ofclaim 26, wherein step (D) includes transferring the resin from theresin source through an opening in one of the susceptors.
 31. The methodof claim 26, wherein step (D) includes flowing excess resin in the moldcavity through an outlet vent in one of the susceptors.
 32. The methodof claim 26, further comprising the step of: (G) quickly exchanging thesusceptors for different susceptors after step (F) has been completed,and then, repeating steps (A) through (F).
 33. A composite part forvehicles molded by the method of claim
 26. 34. An aircraft subassemblymolded by the method of claim 26.